Abstract: To study the impact and fatigue properties of composite stiffened panels, which are widely used in aircraft vertical tail, the multi-impact, high cycle fatigue and residual compressive strength tests were designed based on the composite stiffened panels. The effects of different impact energy on impact damage of stiffener edge were discussed, and damage area development condition under fatigue load of low stress level was also studied. The effect of fatigue on residual compressive strength after impact was given. Results show that the damage areas and dent depth of 40 J impact energy are large, and the damage morphologies of C-scan test are more irregular. The new damage is promoted from main damage area after one million low stress fatigue, and the crack induced by compression failure is propagated to the top and bottom fixed jig. The stiffened panels exhibit better impact and fatigue damage resistance since the retention rate of breaking load after fatigue is about 95.6%. The results can be used for durability and postbuckling design of stiffened panels.